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GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.25 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe155-il-1000000.txt
Download as CSV file: xf-goe155-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 155 (SSW D.1) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3589   0.10323   0.10170  -0.0136   0.9557   0.0109
  -8.500  -0.3581   0.09932   0.09776  -0.0138   0.9425   0.0110
  -8.250  -0.3523   0.09646   0.09488  -0.0139   0.9314   0.0111
  -8.000  -0.3460   0.09384   0.09224  -0.0145   0.9202   0.0113
  -7.750  -0.3393   0.09121   0.08958  -0.0156   0.9083   0.0114
  -7.500  -0.3324   0.08855   0.08687  -0.0169   0.8957   0.0117
  -7.250  -0.3231   0.08569   0.08397  -0.0192   0.8833   0.0121
  -7.000  -0.3101   0.08241   0.08065  -0.0226   0.8709   0.0129
  -6.750  -0.2877   0.07748   0.07565  -0.0314   0.8581   0.0141
  -6.500  -0.2667   0.07297   0.07108  -0.0379   0.8470   0.0142
  -6.250  -0.2454   0.06869   0.06672  -0.0429   0.8371   0.0142
  -6.000  -0.1912   0.04893   0.04695  -0.0436   0.8002   0.0147
  -5.750  -0.1746   0.04612   0.04409  -0.0457   0.7927   0.0151
  -5.500  -0.1555   0.04271   0.04062  -0.0490   0.7850   0.0157
  -5.250  -0.1337   0.03885   0.03670  -0.0531   0.7783   0.0167
  -5.000  -0.0967   0.03282   0.03052  -0.0621   0.7732   0.0182
  -4.750  -0.0703   0.02830   0.02587  -0.0662   0.7679   0.0182
  -3.750   0.0238   0.03239   0.02935  -0.0787   0.7610   0.0209
  -3.500   0.0618   0.02898   0.02567  -0.0804   0.7553   0.0233
  -3.250   0.0944   0.02084   0.01690  -0.0830   0.7507   0.0240
  -3.000   0.1213   0.01954   0.01553  -0.0836   0.7446   0.0246
  -2.750   0.1487   0.01861   0.01448  -0.0840   0.7380   0.0252
  -2.500   0.1770   0.01748   0.01321  -0.0844   0.7314   0.0262
  -2.250   0.2061   0.01628   0.01179  -0.0846   0.7245   0.0284
  -2.000   0.2359   0.01645   0.01178  -0.0844   0.7184   0.0301
  -1.750   0.2649   0.01291   0.00780  -0.0851   0.7125   0.0320
  -1.500   0.2931   0.01232   0.00713  -0.0853   0.7061   0.0330
  -1.250   0.3218   0.01177   0.00650  -0.0855   0.6990   0.0345
  -1.000   0.3504   0.01130   0.00590  -0.0856   0.6917   0.0364
  -0.750   0.3792   0.01193   0.00649  -0.0855   0.6825   0.0389
  -0.500   0.4076   0.01026   0.00466  -0.0860   0.6744   0.0437
  -0.250   0.4375   0.00893   0.00307  -0.0856   0.6661   0.0319
   0.000   0.4662   0.00857   0.00266  -0.0857   0.6577   0.0317
   0.500   0.5232   0.00806   0.00207  -0.0858   0.6374   0.0320
   0.750   0.5518   0.00791   0.00188  -0.0860   0.6252   0.0320
   1.000   0.5802   0.00780   0.00172  -0.0861   0.6105   0.0320
   1.250   0.6086   0.00773   0.00158  -0.0862   0.5926   0.0328
   1.500   0.6369   0.00772   0.00150  -0.0863   0.5713   0.0329
   1.750   0.6650   0.00777   0.00145  -0.0864   0.5457   0.0332
   2.000   0.6929   0.00788   0.00143  -0.0865   0.5173   0.0339
   2.250   0.7208   0.00800   0.00144  -0.0866   0.4902   0.0358
   2.500   0.7487   0.00813   0.00148  -0.0867   0.4678   0.0378
   2.750   0.7765   0.00826   0.00154  -0.0868   0.4499   0.0405
   3.000   0.8044   0.00836   0.00165  -0.0869   0.4347   0.0701
   3.250   0.8321   0.00840   0.00181  -0.0870   0.4184   0.1600
   3.500   0.8557   0.00699   0.00209  -0.0867   0.4014   1.0000
   3.750   0.8833   0.00717   0.00221  -0.0867   0.3874   1.0000
   4.000   0.9106   0.00739   0.00233  -0.0868   0.3697   1.0000
   4.250   0.9379   0.00761   0.00248  -0.0868   0.3478   1.0000
   4.500   0.9647   0.00790   0.00264  -0.0868   0.3217   1.0000
   4.750   0.9911   0.00826   0.00284  -0.0868   0.2910   1.0000
   5.000   1.0172   0.00864   0.00309  -0.0867   0.2636   1.0000
   5.250   1.0434   0.00899   0.00333  -0.0867   0.2429   1.0000
   5.750   1.0957   0.00963   0.00381  -0.0865   0.2106   1.0000
   6.000   1.1215   0.00998   0.00408  -0.0864   0.1892   1.0000
   6.500   1.1608   0.01253   0.00576  -0.0847   0.0304   1.0000
   6.750   1.1851   0.01304   0.00627  -0.0843   0.0244   1.0000
   7.000   1.2102   0.01339   0.00665  -0.0840   0.0222   1.0000
   7.250   1.2341   0.01391   0.00719  -0.0836   0.0191   1.0000
   7.500   1.2577   0.01443   0.00776  -0.0831   0.0172   1.0000
   7.750   1.2819   0.01482   0.00817  -0.0827   0.0159   1.0000
   8.000   1.3055   0.01527   0.00865  -0.0822   0.0147   1.0000
   8.250   1.3263   0.01606   0.00950  -0.0813   0.0132   1.0000
   8.500   1.3466   0.01684   0.01037  -0.0804   0.0125   1.0000
   8.750   1.3687   0.01735   0.01093  -0.0797   0.0119   1.0000
   9.000   1.3903   0.01789   0.01150  -0.0790   0.0112   1.0000
   9.250   1.4112   0.01844   0.01208  -0.0782   0.0105   1.0000
   9.500   1.4303   0.01914   0.01283  -0.0772   0.0100   1.0000
   9.750   1.4414   0.02050   0.01429  -0.0750   0.0093   1.0000
  10.000   1.4499   0.02192   0.01584  -0.0725   0.0089   1.0000
  10.250   1.4645   0.02267   0.01666  -0.0708   0.0087   1.0000
  10.500   1.4740   0.02359   0.01765  -0.0684   0.0085   1.0000
  10.750   1.4815   0.02473   0.01888  -0.0660   0.0083   1.0000
  11.000   1.4888   0.02598   0.02023  -0.0638   0.0080   1.0000
  11.250   1.4957   0.02735   0.02169  -0.0618   0.0078   1.0000
  11.500   1.5025   0.02881   0.02323  -0.0601   0.0076   1.0000
  11.750   1.5101   0.03027   0.02476  -0.0586   0.0073   1.0000
  12.000   1.5188   0.03169   0.02624  -0.0574   0.0071   1.0000
  12.250   1.5253   0.03335   0.02797  -0.0562   0.0069   1.0000
  12.500   1.5268   0.03558   0.03027  -0.0548   0.0066   1.0000
  12.750   1.5183   0.03891   0.03374  -0.0529   0.0064   1.0000
  13.000   1.5052   0.04288   0.03789  -0.0508   0.0062   1.0000
  13.250   1.5087   0.04516   0.04028  -0.0501   0.0062   1.0000
  13.500   1.5113   0.04761   0.04284  -0.0495   0.0061   1.0000
  13.750   1.5118   0.05033   0.04568  -0.0489   0.0060   1.0000
  14.000   1.5103   0.05335   0.04882  -0.0485   0.0059   1.0000
  14.250   1.5074   0.05661   0.05221  -0.0481   0.0058   1.0000
  14.500   1.5033   0.06008   0.05582  -0.0479   0.0057   1.0000
  14.750   1.4981   0.06388   0.05975  -0.0479   0.0056   1.0000
  15.000   1.4916   0.06797   0.06398  -0.0481   0.0055   1.0000
  15.250   1.4845   0.07229   0.06844  -0.0487   0.0055   1.0000
  15.500   1.4760   0.07699   0.07329  -0.0496   0.0054   1.0000
  15.750   1.4666   0.08201   0.07846  -0.0507   0.0054   1.0000
  16.000   1.4559   0.08736   0.08397  -0.0522   0.0053   1.0000
  16.250   1.4435   0.09317   0.08993  -0.0541   0.0053   1.0000
  16.500   1.4310   0.09922   0.09614  -0.0563   0.0052   1.0000
  16.750   1.4165   0.10576   0.10283  -0.0589   0.0052   1.0000
  17.000   1.4016   0.11257   0.10980  -0.0618   0.0052   1.0000
  17.250   1.3847   0.12002   0.11741  -0.0652   0.0052   1.0000
  17.500   1.3646   0.12837   0.12593  -0.0694   0.0052   1.0000
  17.750   1.3433   0.13731   0.13505  -0.0741   0.0052   1.0000
  18.000   1.3221   0.14674   0.14464  -0.0794   0.0052   1.0000
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